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MAINTENANCE MANUAL
(d) Transition to Rollout Arm 1) When autoland status is ROLLOUT ARM and the left FCC is LOCAL FIRST IN CMD, and the yaw channel remains in sync.
2) Each of the remaining FCCs (R and C) detects that the L FCC is CMDENG and each must receive individual CMDENG requests. The LOCAL FIRST IN CMD logic for the C and R FCCs is zero. The MULTIARM 1/2 logic is generated in the C FCC and R FCC. Both C and R multichannel engage (MCHENG) logic outputs are zero until MCHENG occurs. The R and C FCCs remain ARMED for CMDENG and are also ROLLOUT ARMED.
3) Multi-channel engage requires G/S and LOC capture and an indication of less than 1500 feet from a valid radio altimeter. Engage logic in the L FCC generates MCHENG (multichannel engage). In the C and R FCCs, engage logic generates MCHENG and C or R CMDENG logic. At MCHENG, the L FCC causes the yaw channel to be in CMD. The C FCC and R FCC cause roll, pitch and yaw to be in CMD. All three FCCs are now in ROLLOUT ENGAGE.
(e) Rollout Engage Default to OFF
1) Rollout engage defaults to OFF occurs when an engage removal fault is detected from the engage interlocks (Ref 22-11-00). If the L FCC defaults to OFF, for example, L CMDENG is logic zero to all FCCs. Sequence detection logic then selects a new LOCAL FIRST IN CMD from a prescribed sequence. This channel controls the ASA display.
(24) Autoland Flight Path Control Signal Flow and Monitoring (Fig. 10)
(a)
Autoland pitch signals provide control during the following positions of the flight profile: 1) Glideslope (less than 1500 feet) 2) Flare (from gear altitude at 50 feet to touchdown) 3) Nose wheel let down 4) Elevator Equalization
(b)
At multi-channel engage, elevator equalization logic becomes valid. The elevator commands are adjusted to remove any small errors between surface position feedback and servo position feedback.
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FAULT ISOLATION/MAINT MANUAL
AUTOPILOT/FLIGHT DIRECTOR PITCH CHANNEL
COMPONENT SHT 102 FIG. QTY ACCESS/AREA REFERENCE AMM
SERVO - C AUTOPILOT PITCH CONTROL, M272 1 1 313BL, SECT 48 22-12-01
SERVO - L AUTOPILOT PITCH CONTROL, M271 1 1 313BL, SECT 48 22-12-01
SERVO - R AUTOPILOT PITCH CONTROL, M273 1 1 313BL, SECT 48 22-12-01
1TS15 TRANSDUCER - L ELEVATOR CONTROL FORCE, 2 1 113AL, FWD EQUIP CTR 22-12-03
1TS14 TRANSDUCER - R ELEVATOR CONTROL FORCE, 2 1 113AL, FWD EQUIP CTR 22-12-03
TRANSDUCER - C ELEVATOR NEUTRAL SHIFT, TS5153 2 1 313BL, SECT 48 22-12-04
TRANSDUCER - L ELEVATOR NEUTRAL SHIFT, TS5151 2 1 313BL, SECT 48 22-12-04
TRANSDUCER - R ELEVATOR NEUTRAL SHIFT, TS5152 2 1 313BL, SECT 48 22-12-04
VALVE - ELECTROHYDRAULIC SERVO 2 1 PITCH CONTROL SERVO 313BL, SECT 48, EA AUTOPILOT 22-12-02
VALVE - ELECTROHYDRAULIC SOLENOID 2 2 PITCH CONTROL SERVO 313BL, SECT 48, EA AUTOPILOT 22-12-02
AIRPLANES WITH CONTROL WHEEL STEERING
Autopilot/Flight Director Pitch Channel - Component Index
Figure 101
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FAULT ISOLATION/MAINT MANUAL
ACCESS PANEL, 313BL
AUTOPILOT PITCH CONTROL SERVO LOCATIONS AND LINKAGES (REF)
SEE A
TORQUE
TUBES
(REF)
TORQUE BOX (REF)
LEFT APCS, M271
SEE B SHT 2
CENTER APCS, M272
SEE B SHT 2
CONTROL RODS (REF)
RIGHT APCS, M273
SEE B SHT 2
CONTROL FEEL AND CENTERING
ROD (REF) UNIT ASSEMBLY (REF) FWDSEE C SHT 2
AUTOPILOT PITCH CONTROL SERVO
OUTBD LOCATIONS AND LINKAGES (REF)
A
Autopilot/Flight Director Pitch Channel - Component Location
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